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基于SDRE具有终端碰撞角约束的非线性微分对策制导律
引用本文:李伟,黄瑞松,王芳,崔乃刚.基于SDRE具有终端碰撞角约束的非线性微分对策制导律[J].系统工程与电子技术,2016,38(7):1606-1613.
作者姓名:李伟  黄瑞松  王芳  崔乃刚
作者单位:1. 哈尔滨工业大学航天学院, 黑龙江 哈尔滨 150001;; 2. 中国航天科工集团飞航技术研究院, 北京 100074
摘    要:通过非线性微分对策理论讨论了具有终端碰撞角约束的弹目追逃问题,提出了基于求解状态相关黎卡提方程(state dependent Riccati equation,SDRE)的方法解决该微分对策问题,得到了具有终端碰撞角约束的SDRE解析解。提出的终端碰撞角约束制导律是以弹目视线角速率及碰撞角误差为状态向量进行推导,并研究了闭环系统局部渐进稳定的条件。该制导律不需要进行剩余时间的预测。最后针对目标不进行机动、进行阶跃机动、正弦机动及目标最优机动形式4种情况,进行了制导律的仿真验证,仿真结果表明该制导律对于不同机动目标均具有良好的制导效果且能很好地满足末端碰撞角约束要求。


Nonlinear differential games guidance law based on SDRE with terminal impact angular
LI Wei,HUANG Rui-song,WANG Fang,CUI Nai-gang.Nonlinear differential games guidance law based on SDRE with terminal impact angular[J].System Engineering and Electronics,2016,38(7):1606-1613.
Authors:LI Wei  HUANG Rui-song  WANG Fang  CUI Nai-gang
Institution:1. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China; 2. Hiwing TechnologyAcademy of China Aerospace Science and Industry Corporation, Beijing 100074, China
Abstract:The problem of intercepting a maneuvering target at a terminal impact angular is discussed in the nonlinear differential games framework. A feedback form solution is proposed by extending the state dependent Riccati equation (SDRE) method to nonlinear zero sum differential games. An analytic solution is obtained for the SDRE corresponding to the impact angle constrained guidance problem. The impact angle constrained guidance law is derived using the line-of-sight rate and projected terminal impact angle error as the state vectors. Local asymptotic stability conditions for the closed loop system corresponding to these states are studied. Time to go estimation is not explicitly required to derive and implement the proposed guidance law. Finally, through mathematical simulations, the derived guidance law is tested under four scenarios of target maneuvering: nonmaneuvering, step maneuvering, sine maneuvering and the best control maneuvering. The simulation results show that the guidance law have good effects for different maneuvering targets and can satisfy terminal impact angular constraint requirements.
Keywords:
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